Published November 14, 2014
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Transonic Limits of Linearized Theory
- Creators
- Cole, J. D.
Abstract
The transonic regime, extending from Mach numbers at which shock waves first appear with the associated drag rise to Mach numbers at which the head shock wave is firmly attached to the nose of the body, is well known. Not so well known, perhaps, is the reason for the failure of linearized theory to describe the flow in this regime, in particular, to permit an accurate calculation of the pressure.
Additional Information
© 1954 California Institute of Technology. OSR Technical Note 228. Contract AF-18(600)-383 Air Research and Development Command.Attached Files
Submitted - OSRtn228.pdf
Files
OSRtn228.pdf
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Additional details
- Eprint ID
- 51766
- Resolver ID
- CaltechAUTHORS:20141114-104653926
- AF-18(600)-383
- Air Force Office of Scientific Research (AFOSR)
- Created
-
2014-11-14Created from EPrint's datestamp field
- Updated
-
2021-11-22Created from EPrint's last_modified field
- Caltech groups
- Graduate Aeronautical Laboratories (Fluid Mechanics), GALCIT
- Other Numbering System Name
- OSR Technical Note
- Other Numbering System Identifier
- 228